EP2878503B1 - Système de freinage électrique d'avion - Google Patents

Système de freinage électrique d'avion Download PDF

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Publication number
EP2878503B1
EP2878503B1 EP14195206.9A EP14195206A EP2878503B1 EP 2878503 B1 EP2878503 B1 EP 2878503B1 EP 14195206 A EP14195206 A EP 14195206A EP 2878503 B1 EP2878503 B1 EP 2878503B1
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EP
European Patent Office
Prior art keywords
emergency
motor controller
brake
normal
motor
Prior art date
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Active
Application number
EP14195206.9A
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German (de)
English (en)
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EP2878503A1 (fr
Inventor
George Iordanidis
John Rees
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Airbus Operations Ltd
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Airbus Operations Ltd
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Publication date
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Priority to PL14195206T priority Critical patent/PL2878503T3/pl
Publication of EP2878503A1 publication Critical patent/EP2878503A1/fr
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T13/00—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems
    • B60T13/74—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive
    • B60T13/741—Transmitting braking action from initiating means to ultimate brake actuator with power assistance or drive; Brake systems incorporating such transmitting means, e.g. air-pressure brake systems with electrical assistance or drive acting on an ultimate actuator
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
    • B60T8/17—Using electrical or electronic regulation means to control braking
    • B60T8/1701—Braking or traction control means specially adapted for particular types of vehicles
    • B60T8/1703—Braking or traction control means specially adapted for particular types of vehicles for aircrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T8/00—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force
    • B60T8/32—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration
    • B60T8/321—Arrangements for adjusting wheel-braking force to meet varying vehicular or ground-surface conditions, e.g. limiting or varying distribution of braking force responsive to a speed condition, e.g. acceleration or deceleration deceleration
    • B60T8/325—Systems specially adapted for aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B64C25/44—Actuating mechanisms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B64C25/44—Actuating mechanisms
    • B64C25/46—Brake regulators for preventing skidding or aircraft somersaulting
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T2270/00—Further aspects of brake control systems not otherwise provided for
    • B60T2270/40—Failsafe aspects of brake control systems
    • B60T2270/404—Brake-by-wire or X-by-wire failsafe
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T2270/00—Further aspects of brake control systems not otherwise provided for
    • B60T2270/40—Failsafe aspects of brake control systems
    • B60T2270/413—Plausibility monitoring, cross check, redundancy

Definitions

  • the present invention relates to an electrically actuated braking system for an aircraft.
  • Electric systems are gradually replacing hydraulic systems on many commercial, and military, aircraft.
  • Current "brake by wire” aircraft systems may have a generally centralised architecture in which pilot inputs are interpreted and command and monitoring signals are communicated via a databus and as analogue/discrete signals to a brake control unit (BCU).
  • BCU brake control unit
  • An exemplary centralised architecture is described in US 2008/0030069 A1 .
  • the BCU interprets the commands from the aircraft cockpit controls and avionics and calculates braking force commands for each actuated landing gear wheel of the aircraft. This may include fast loop anti-skid control.
  • Each braking wheel will have at least one electro-mechanical actuator (EMA) for providing a clamping force to the brake for that wheel, which converts the clamping force to a braking torque.
  • Electro-mechanical actuator controllers may be disposed within the landing gear bay and electrically connected to a plurality of brake EMAs coupled to wheel and brake groups.
  • each wheel and brake group includes a plurality of brake EMAs coupled via a brake assembly to a wheel.
  • the EMACs interpret the brake force commands from the BCU and receive electrical power to provide power to drive the EMAs.
  • the plurality of BCUs may be arranged for redundancy and/or fault tolerance.
  • the BCUs may be assigned to particular sides, e.g. aircraft avionics network side or electrical power network side.
  • the EMACs may therefore receive brake force commands from any BCU.
  • the EMACs may all be identical so as to minimise the cost and complexity of design, manufacture, installation, repair, replacement, etc. of parts. There is a therefore a potential for simultaneous failure of several EMACs leading to partial or full loss of braking control, which is undesirable.
  • the EMAC may be considered a "complex" part, i.e. it is not fully testable, as defined in ARP4754.
  • US 2011/0155521 describes an asymmetric electric braking architecture comprising a brake control unit (BCU), electro-mechanical actuators (EMACs), at least one emergency brake power and control unit (EBPCU) and protection means for channelling power supplied by the EMACs or the EBPCU towards the actuators while preventing power from being diverted towards the architecture.
  • BCU brake control unit
  • EMACs electro-mechanical actuators
  • EBPCU emergency brake power and control unit
  • EP 1484244 describes a braking system with at least one brake actuator, and a plurality of brake controllers configured to function redundantly so as to provide the drive control signals to effect the braking torque even in the event that one of the plurality of brake controllers becomes inoperative.
  • the English Patent GB2444630 discloses in an embodiment of an electric brake system a distribution of wheel brake and parking brake control into four independent channels on two line replaceable units (LRUs). Each of these independent channels/modules receives its own set of inputs (e.g., brake pedal deflection data and parking brake lever status data) and, in turn, independently commands the activation of the parking brake mechanisms for the wheels. it however does not disclose LRUs which integrate the electro-mechanical brakes together with the controllers.
  • LRUs which integrate the electro-mechanical brakes together with the controllers.
  • the invention provides an electrically actuated braking system for an aircraft, comprising: an electro-mechanical brake actuator (EMAbrake) proximate a wheel of the aircraft, the EMAbrake including a motor; an electro-mechanical actuator controller (EMAC) including a motor controller for generating a drive signal for the EMAbrake; and a braking control unit for generating a braking force command signal for the EMAC; wherein the braking control unit and the EMAC are disposed together with the EMAbrake in a common line replaceable unit (LRU).
  • EMAbrake electro-mechanical brake actuator
  • EMAC electro-mechanical actuator controller
  • LRU common line replaceable unit
  • the invention is advantageous in that the common LRU enables reduced wiring complexity to the EMAbrake, providing weight and cost savings and enhanced reliability compared to previous electrically actuated braking systems.
  • the braking control unit may be at least one of: a normal mode braking control unit (BCU) configured to generate a braking force command signal for the EMAC during a normal mode of operation; and an emergency mode braking control unit (eBCU) configured to generate a braking force command signal for the EMAC during an emergency mode of operation.
  • BCU normal mode braking control unit
  • eBCU emergency mode braking control unit
  • the BCU and/or the eBCU may be operable to perform anti-skid brake control.
  • the system includes at least one normal mode braking control unit (BCU) configured to generate a braking force command signal for the EMAC during a normal mode of operation; and at least one an emergency mode braking control unit (eBCU) configured to generate a braking force command signal for the EMAC during an emergency mode of operation.
  • BCU normal mode braking control unit
  • eBCU emergency mode braking control unit
  • the common LRU has one or more BCUs but no eBCU
  • one or more eBCUs may be disposed remote from the LRU.
  • the common LRU has at least one BCU and at least one eBCU.
  • the EMAC may include a plurality of motor controllers.
  • the EMAC may include a first motor controller for generating a first drive signal for the EMAbrake, and a second motor controller for generating a second drive signal for the EMAbrake.
  • the first motor controller and the second motor controller may each comprise hardware for generating a pulse-width modulation signal.
  • the first motor controller and the second motor controller may include similar hardware for generating a pulse-width modulation signal.
  • the first motor controller and the second motor controller may include dissimilar hardware for generating a pulse-width modulation signal so as to provide protection against common mode failure of the first and second motor controllers.
  • the first motor controller and the second motor controller may each comprise similar or dissimilar hardware selected from the group comprising: a microprocessor, a microcontroller, a digital signal processor, an application specific integrated circuit, a programmable logic device, a complex programmable logic device, a field programmable gate array, and a transistor based discrete electronics switching circuit.
  • the BCU may be operable on a normal brake channel, and the eBCU may be operable on an emergency brake channel.
  • the first motor controller may be operable on a normal motor control channel, and the second motor controller may be operable on an emergency motor control channel.
  • the BCU may be configured to communicate with the first motor controller and not the second motor controller, and the eBCU may be configured to communicate with the second motor controller and not the first motor controller.
  • the normal brake channel and the normal motor control channel may be coupled so as to form a normal channel
  • the emergency brake channel and the emergency motor control channel may be coupled so as to form an emergency channel
  • the system may further comprise a switch for switching between the normal channel and the and emergency channel.
  • the BCU may be configured to communicate with either the first motor controller or the second motor controller
  • the eBCU may be configured to communicate with either the first motor controller or the second motor controller.
  • a first switch may be provided for switching between the normal and emergency brake channels, and a second switch may be provided for switching between the normal and emergency motor control channels.
  • the first switch and the second switch may be independently switchable.
  • a source switch may be operatively coupled between the normal and emergency motor control channels and the EMAbrake for switching the EMAbrake control depending on the selected motor control channel.
  • an OR gate may be operatively coupled between the normal and emergency motor control channels and the EMAbrake for controlling the EMAbrake depending on the operative motor control channel.
  • the BCU may include redundant brake control channels each for communicating with aircraft cockpit controls and avionics via a respective databus.
  • an aircraft including the electrically actuated braking system above.
  • a plurality of the common LRUs may be associated with a braked wheel of the aircraft, i.e. a wheel brake assembly for a landing gear wheel may be actuated by a plurality of the EMAbrakes, each EMAbrake forming part of the respective common LRU also having the EMAC and BCU and/or eBCU.
  • the anti-skid control may be at an EMAbrake level not on a per wheel basis.
  • the anti-skid control may be synchronized between all of the EMAbrakes (LRUs) associated with the respective braked wheel. The synchronization requires communication between the EMAbrakes associated with the respective braked wheel.
  • the common LRU may be configured to handle only digital communications external to the LRU, e.g. via a digital databus, and not analogue communications.
  • the electrically actuated braking system may further include a router for routing digital communications between aircraft cockpit controls and aircraft avionics and the fully smart EMA.
  • the router may be located at the base of a landing gear leg, i.e. adjacent the axle/slider of the landing gear.
  • the electrically actuated aircraft braking system 100 of the first embodiment shown in figure 1 is configured for an aircraft having two braked main landing gears, one on either side of the aircraft centre line.
  • the invention described herein relates to any aircraft configuration having braking wheels, including aircraft with more than two main landing gears and/or braked nose landing gear.
  • the braking system 100 features fully distributed avionics.
  • the braking system 100 includes aircraft cockpit controls and aircraft avionics 110 which communicates via databuses 111, 112 and routers 131-138 with "fully smart" electro-mechanical brake actuators (EMAs) 151a-d, 152a-d, 153a-d, and 154a-d (described in detail below) associated with wheel and brake groups 161-164.
  • EMAs electro-mechanical brake actuators
  • wheel and brake groups 161-164 there are four wheel and brake groups (one per wheel of two diablo main landing gears), and four fully smart EMAs per wheel and brake group.
  • Electric brake power supply units 181-184 are arranged to supply power to the fully smart EMAs.
  • the braking system 100 comprises both a normal and an emergency system.
  • the normal system includes dual redundant brake control units (BCUs) 121, 122 assigned to particular sides, e.g. aircraft avionics network or electrical power network sides (side1, side2, etc.).
  • the emergency system includes an emergency BCU (eBCU) 123.
  • the eBCU 123 provides protection against the loss of function of both BCUs 121, 122, e.g. from failure of the BCUs, failure of the aircraft avionics, failure of the communications databus, and also possibly failure of a power supply (depending on the power supply configuration) - all of which could lead to a loss of function for the BCU.
  • the fully smart EMAs 151a-d, 152a-d, 153a-d and 154a-d each include, in addition to the brake EMA 191, the side1 BCU, side2 BCU and eBCU function blocks packaged together with EMA controller (EMAC) function blocks within a single line replaceable unit (LRU).
  • EEC EMA controller
  • the BCUs 121, 122 receive input from aircraft cockpit controls and avionics 110 via databus 111 and the eBCUs 123 receive input from aircraft cockpit controls and avionics 110 via databus 112.
  • the databus 112 may be dissimilar to the databus 111.
  • the databus 112 may be replaced by routes carrying analogue and/or discrete signals, e.g. from a brake pedal transmitter unit (BPTU) indicating a brake pedal angle.
  • BPTU brake pedal transmitter unit
  • databus 111 In the configuration shown in figures 1 and 2 only databus 111 (and not databus 112) is operable during the normal mode of operation.
  • the databus 111 In the emergency mode of operation the databus 111 is inactive and the databus 112 is active.
  • the emergency databus may have reduced functionality (e.g. slower speed) as compared with the normal mode databus.
  • the databuses 111 and 112 may be switched so that only one of databus 111 and databus 112 is active at any time but databus 111 may be used in the normal and the emergency modes and similarly databus 112 may be used in the normal and the emergency modes.
  • the BCUs 121, 122 interpret signals from the aircraft cockpit controls and avionics 110 and issue braking force commands on a per wheel basis to motor controllers within the EMAC function block 141 of the respective fully smart EMA.
  • the routers 131-138 route digital databus signals from the aircraft cockpit controls and aircraft avionics 110 to the fully smart EMAs (and vice versa).
  • the four fully smart EMAs associated with each wheel and brake group communicate via a first router with databus 111 and via a second router with databus 112.
  • communications between the aircraft cockpit controls and aircraft avionics 110 and the four EMAs 151a-d of wheel and brake group 1 (161) in the normal mode are routed via databus 111 and router 131.
  • Communications between the aircraft cockpit controls and aircraft avionics 110 and the four EMAs 151a-d of wheel and brake group 1 (161) in the emergency mode are routed via databus 112 and router 133.
  • each wheel and brake group is associated with four fully smart EMAs, and two routers - one normal mode router which communicates via normal mode databus 111 and one emergency mode router which communicates via emergency mode databus 112.
  • the EMAC function blocks 141 of each fully smart EMA include motor controllers 145, 146 and a power inverter stage 147.
  • the motor controllers 145, 146 interpret brake force commands from the BCUs 121, 122 and generate a drive signal for the EMA 191.
  • the power stage 147 powers the EMA 191 and is electrically connected to the aircraft power networks N1, N2 (note only the high voltage parts of the aircraft power networks N1, N2 are shown in figure 1 ) via the EBPSUs.
  • the EBPSUs may include a safety power interlock, and may further include power source switching and/or power conversion, if required.
  • the EMAC function block 141 therefore provides power and control signals to drive the EMA 191 within each fully smart EMA.
  • the BCUs 121, 122 within each fully smart EMA perform fast loop anti-skid control for their respective wheel and brake on a per EMA basis.
  • the anti-skid control between each of the four EMAs associated with the same wheel and brake may be synchronised.
  • the EMAs may communicate directly with each other or may route communications via the databus network. In some circumstances synchronisation of anti-skid control between fully smart EMAs associated with the same wheel and brake may not be required.
  • the EMA 191 of each fully smart EMA converts the electrical power from the EBPSUs into mechanical power to provide a clamping force to the brake associated with its respective wheel.
  • the wheel and brake assembly converts the clamping force applied by the EMA into braking torque so as to decelerate or hold stationary the aircraft.
  • the EMAC function blocks 141 of each fully smart EMA include a primary, or first, motor controller for driving the motor of the EMA 191 with which it is associated.
  • the EMAC function blocks further comprise a secondary, or second, motor controller.
  • the primary motor controller forms part of a normal channel of the EMAC function blocks
  • the secondary motor controller forms part of an emergency channel of the EMAC function blocks.
  • the motor controller is the complex part of the EMAC function blocks, and so a dissimilar motor controller is incorporated within the EMAC function blocks to form part of the emergency channel.
  • the eBCU 123 within each fully smart EMA outputs brake control signals for the respective wheel and brake 161, 162, 163, 164 with which it is associated.
  • the eBCU 123 is operable to perform the same functions as the BCUs 121, 122 but is in use only when the system is in emergency mode.
  • the eBCU 123 may comprise simpler technology, or may receive and output analogue signals only depending on the architecture.
  • the eBCU 123 preferably performs fast loop anti-skid control for the braking wheel of the wheel and brake group with which it is associated.
  • the eBCU may be based upon dissimilar technology to the BCU for protection against common mode failures.
  • the eBCU anti-skid control where provided, is on a per EMA basis and so anti-skid control synchronisation between fully smart EMAs associated with the same wheel and brake may be required as explained above with reference to the BCUs.
  • Figure 2 illustrates schematically the physical arrangement of the four fully smart EMAs 151a-d in the brake assembly of the wheel and brake 161.
  • the fully smart EMAs 151a and 151b are powered by aircraft power network N2 (via EBPSU 182) and the fully smart EMAs 151c and 151d are powered by aircraft power network N1 (via EBPSU 181).
  • Communications between the aircraft cockpit controls and aircraft avionics and all four fully smart EMAs 151a-d are routed either via databus 111 and router 131, or via databus 112 and router 133.
  • the databus 111 and router 131 are designated for the normal mode and databus 112 and router 133 are designated for the emergency mode in this configuration.
  • Router 131 communicates with each of the four fully smart EMAs 151a-d and router 133 communicates with each of the four fully smart EMAs151a-d.
  • the routers 131, 133 are located at or adjacent the bottom of the landing gear leg, e.g. on the slider/axle or adjacent the wheel with which they are associated. This significantly reduces the wiring weight and complexity of the braking system since the databuses 111, 112 can be run all the way down the landing gear leg from the landing gear bay.
  • the environment at the bottom of the landing gear leg is particularly harsh and so in some circumstances it may be desirable to locate the routers in the landing gear bay or in the avionics bay or in another location within the aircraft remote from the bottom of the landing gear leg. In such circumstances it may be necessary to provide relatively long local databus cabling runs between the routers and each of the fully smart EMAs so increasing the wiring complexity and therefore weight and cost as compared with the configuration shown in figure 2 .
  • the fully smart EMAs are preferably capable of handling only digital communications with the aircraft cockpit controls and aircraft avionics. This is a significant departure from previous EMAs which require analogue communications.
  • the ability of the fully smart EMAs to handle only digital communications combined with locating the routers at the bottom of the landing gear leg means that only digital databuses are required down the landing gear leg, which reduces wiring weight, complexity and cost and improves reliability.
  • the fully smart EMAs could alternatively communicate with the aircraft cockpit controls and aircraft avionics via analogue routes.
  • the fully smart EMAs capable of handling only digital communications beneficially contributes to lowering the maintenance requirement of the braking system since each fully smart EMA need only be connected via a local databus (to the routers) and a power cable (to the aircraft power network/braking power supply).
  • the fully smart EMA is therefore a plug and play device.
  • Each of the fully smart EMAs in the braking system are preferably identical so as to reduce parts count and inventory requirements.
  • the fully smart EMAs include hardware arranged to provide the requisite redundancy by dissimilar technologies as will be described below.
  • FIG 3 illustrates a schematic of the control of a single fully smart EMA 151a in the first embodiment.
  • the fully smart EMA includes EMA 191, EMAC 141, side 1 and side 2 BCUs 121, 122 and eBCU 123.
  • the EMAC and BCU/eBCU are operable to compute brake force commands on a per wheel basis based on the databus 111, 112 signals from the aircraft cockpit control and avionics 110.
  • the fully smart EMA 151a also receives electrical power from power network N2, as discussed above.
  • power network N2 as discussed above.
  • FIG 4 illustrates schematically the normal and emergency channels within the fully smart EMA 151a.
  • the fully smart EMA includes a side1 BCU function block 121, a side2 BCU function block 122, and a normal (primary) motor controller 145 which is a pulse-width modulation (PWM) signal generator for its associated EMA 191.
  • the fully smart EMA includes an eBCU function block 123 and an emergency (secondary) motor controller 146 which is a PWM signal generator for its EMA 191.
  • the fully smart EMA also includes a power inverter 147 for its EMA 191.
  • the side1 and side 2 BCU function blocks 121, 122 include fast-loop anti skid control.
  • the eBCU function block may or may not also include fast-loop anti skid control.
  • FIG. 5 illustrates a first example of a control scheme for the fully smart EMA 151a shown in Figure 4 .
  • the braking system control is switched 171 unitarily between normal 172 and emergency 173 channels such that the when the brake control channel is switched from the normal channel (though the BCU function block 121/122) to the emergency channel (through the eBCU function block 123) the motor control channel is also switched from the normal channel (through the primary motor controller 145) to the emergency channel (through the secondary motor controller 146).
  • the normal brake control channel always communicates with the normal motor control channel
  • the emergency brake control channel always communicates with the emergency motor control channel.
  • the fully smart EMA further includes a source switch 148 for switching between the normal and emergency channels as both channels may be continuously transmitting.
  • a source switch 148 for switching between the normal and emergency channels as both channels may be continuously transmitting.
  • an OR gate may be used in place of the source switch 148 if the control channels are not continuously transmitting.
  • Figure 6 illustrates a second example of a control scheme for the fully smart EMA 151a (denoted here 151a") shown in Figure 4 .
  • the active brake control channel of the BCU/eBCU function blocks and the active motor control channel of the fully smart EMA may be switched independently depending on failure conditions. Therefore the normal brake control channel (though the BCU 121/122 function blocks) may communicate with either the normal motor channel (through the primary motor controller 145) or the emergency motor channel (through the secondary motor controller 146). Similarly, the emergency brake control channel (though the eBCU function block 123) may communicate with either the normal motor channel (through the primary motor controller 145) or the emergency motor channel (through the secondary motor controller 146).
  • the brake channel control is switched 174 between normal (BCU function block) 172 and emergency (eBCU function block) 173 channels, and the source switch 148 is arranged to switch between the outputs from the normal and emergency motor controllers 145, 146.
  • the fully smart EMA 151a" further includes a source switch 149 for switching 177 the brake control received from either the BCU function blocks 121, 122 or the eBCU function block 123 to either the normal motor control channel 178 or the emergency motor control channel 179.
  • an OR gate may be used in place of the source switches 148, 149 if the control channels are not continuously transmitting.
  • FIG 7 illustrates in detail one exemplary embodiment of the dissimilar motor controllers which may be used in the first example fully smart EMA 151a of Figure 5 .
  • the primary (normal) motor controller (PWM signal generator) 145 is a digital signal processor (DSP)
  • the secondary (emergency) motor controller (PWM signal generator) 146 is a field programmable gate array (FPGA).
  • the source switch 148 is a sextuple 2-channel multiplexer. Feedback signals from the EMA 151a are directed to the primary and secondary controllers 145, 146.
  • Figure 7a illustrates an alternative fully smart EMA (denoted here 151a') similar to the fully smart EMA 151a of figure 7 but in which the source switch 148 has been replaced by an OR gate 148'. In all other respects the fully smart EMA 151a' is identical to the fully smart EMA 151a of figure 7 .
  • Figure 8 illustrates the fully smart EMAC 151a" for use in the second example control scheme of Figure 6 .
  • the normal/emergency brake channel switching 174 is effected by source switch 149, whilst the normal/emergency (primary/secondary) motor control channel switching 177 is effected by source switch 148.
  • Figure 8a illustrates an alternative fully smart EMA (denoted here 151a''') similar to the fully smart EMA 151a" of figure 8 but in which the source switches 148, 149 have been replaced by OR gates 148', 149', as described above, and the brake and motor control channel switching is provided by primary/secondary control enable 174, 177.
  • the fully smart EMA 151a''' is identical to the fully smart EMA 151a" of figure 8 .
  • processor based technologies such as microprocessors, microcontrollers and DSPs
  • logic based devices such as ASIC (application specified integrated circuits), PLD (programmable logic devices), CPLD (complex programmable logic devices) and FPGAs
  • discrete electronics such as transistor based switching circuits for example. Any combination of two similar or dissimilar technologies may be selected for the two motor controllers of the fully smart EMA.
  • braking system 100 Operation of the braking system 100 will now be described.
  • cockpit braking control cockpit signals such as the brake pedal angle
  • command and monitoring signals are sent to the side1 and side2 BCUs 121, 122 of the fully smart EMAs.
  • Discrete signals are also sent to the EBPSU hardware enable and allows high voltage power from the aircraft power networks N1, N2 to be supplied to the power inverter stage 147 of the fully smart EMAs.
  • Either side1 or side2 BCUs 121, 122 of each fully smart EMA compute the brake force required based upon the command signal received from the aircraft avionics and (if available) performs anti-skid computation based upon wheel speeds, before sending a modified braking force command to the normal motor control channel 145 within each fully smart EMA.
  • the normal motor control channel within the fully smart EMA receives the brake force command from the BCUs and (based upon a determination of which BCU is currently active) computes a PWM signal which is sent to the power inverter stage 147 within the fully smart EMA.
  • the power inverter stage uses the PWM signal to modulate the power supply to the EMA 191 of each respective fully smart EMA 151a-d, 152a-d, 153a-d, 154a-d.
  • the EMAs 191 receive the electrical power and produce a clamping force on the respective brakes in order to decelerate or hold stationary the aircraft.
  • the system In the case of a failure in one of the BCUs 121, 122 the system is operable to switch sides to the other active BCU 121, 122.
  • the EBPSU hardware enable receives the braking enable signal and allows high voltage power to be supplied to the power inverter stage 147 within the fully smart EMAs.
  • the eBCU 123 computes the braking force required based upon the command signal received from the aircraft avionics and (if available) performs anti-skid computation based upon wheel speeds, before sending a modified braking force command to the emergency motor control channel 146 within the respective fully smart EMA.
  • the emergency motor control channel within the fully smart EMA receives the brake force command from the eBCU and computes a PWM signal which is sent to the power inverter stage 147 within the fully smart EMA.
  • the power inverter stage uses the PWM signal to modulate the power supply to the respective EMA 191.
  • the EMAs receive the electrical power and produce a clamping force on the respective brakes in order to decelerate the aircraft.
  • the EBPSUs are disposed remote from the fully smart EMAs.
  • the EBPSUs typically have a large capacitor (a filter as part of the power filtering function of the EBPSU) making it generally unsuitable for incorporation within the fully smart EMAs.
  • capacitor technologies will improve such that the EBPSU functionality may be integrated within each fully smart EMA.
  • the number of EBPSUs would however increase from four to sixteen (one per EMA) in the modified version of the system shown in figure 1 and so this option may still not be preferred even with lightweight capacitor technology.
  • the EBPSUs are operable to convert the main and backup aircraft power network voltages to a power supply used by the routers and fully smart EMAs of the braking system.
  • the invention is applicable to a variety of different aircraft power network voltages, e.g. 115V AC, 270V DC, 540V DC and 28V DC backup battery.
  • the EBPSU may include filtering to protect the aircraft power network from the EMAs and power interlocks.
  • Figure 9 illustrates a schematic of the control of a single fully smart EMA 251a of a second embodiment of a fully distributed electrically actuated aircraft braking system architecture.
  • the braking system of the second embodiment shares many similarities with the first embodiment of figures 1-8 and includes the following key difference.
  • the fully smart EMA 251a In place of the fully smart EMAs in which the normal and emergency BCU functionality is packaged within the fully smart EMA in a single line replaceable unit (LRU), the fully smart EMA 251a has only the (normal) side 1 and side 2 BCU 221, 222 functionality incorporated in the LRU whilst the emergency BCU (eBCU) LRU 223 remains separate and remote from the fully smart EMA 251a.
  • the fully smart EMA may be adopted in the architecture of figure 1 with suitable modifications to incorporate the additional eBCU LRU 223.
  • Either a single eBCU LRU may be provided electrically connected to each of the fully smart EMAs, or to a group of the fully smart EMAs; or a plurality of eBCU LRUs may be provided each electrically connected to one or more of the fully smart EMAs.
  • FIG 10 shows the function blocks of the fully smart EMA 251a in detail, and like reference numerals have been used to denote like parts with figures 1-8 , but numbered in the 200 series.
  • the fully smart EMA 251a therefore includes EMAC 241 with motor controllers 245, 246 and power inverter 247, and EMA 291 in addition to the side 1 and side 2 BCUs 221, 222.
  • Figure 11 illustrates a schematic of the control of a single fully smart EMA 351a of a third embodiment of a fully distributed electrically actuated aircraft braking system architecture.
  • the braking system of the third embodiment shares many similarities with the first embodiment of figures 1-8 and includes the following key difference.
  • the fully smart EMA 351a In place of the fully smart EMAs in which the normal and emergency BCU functionality is packaged within the fully smart EMA in a single line replaceable unit (LRU), the fully smart EMA 351a has only the emergency BCU(eBCU) 323 functionality incorporated in the LRU whilst the (normal) side 1 and side 2 BCU 321, 322 LRUs remain separate and remote from the fully smart EMA 351a.
  • the fully smart EMA may be adopted in the architecture of figure 1 with suitable modifications to incorporate the additional BCU LRUs 221, 222.
  • Side 1 and side 2 BCU LRUs may be provided electrically connected to each of the fully smart EMAs, or to a group of the fully smart EMAs; or a plurality of side 1 and side 2 BCU LRUs may be provided each electrically connected to one or more of the fully smart EMAs.
  • FIG 12 shows the function blocks of the fully smart EMA 351a in detail, and like reference numerals have been used to denote like parts with figures 1-8 , but numbered in the 300 series.
  • the fully smart EMA 351a therefore includes EMAC 341 with motor controllers 345, 346 and power inverter 347, and EMA 391 in addition to the eBCU 223.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • Regulating Braking Force (AREA)
  • Braking Systems And Boosters (AREA)
  • Valves And Accessory Devices For Braking Systems (AREA)

Claims (16)

  1. Système de freinage actionné électriquement pour un aéronef, comprenant :
    un actionneur de freinage électromécanique (EMAbrake) à proximité d'une roue de l'avion, l'actionneur de freinage électromécanique (EMAbrake) comprenant un moteur ;
    un dispositif de commande d'actionneur électromécanique (EMAC) comprenant un dispositif de commande de moteur pour générer un signal d'entraînement pour l'actionneur de freinage électromécanique (EMAbrake) ; et
    une unité de commande de freinage pour générer un signal de commande de force de freinage pour le dispositif de commande d'actionneur électromécanique (EMAC) ;
    caractérisé en ce que l'unité de commande de freinage et le dispositif de commande d'actionneur électromécanique (EMAC) sont disposés ensemble avec l'actionneur de freinage électromécanique (EMAbrake) dans une unité remplaçable en escale commune (LRU).
  2. Système de freinage actionné électriquement selon la revendication 1, l'unité de commande de freinage pouvant fonctionner pour effectuer une commande de freinage antidérapage.
  3. Système de freinage actionné électriquement selon l'une quelconque des revendications précédentes, l'unité de commande de freinage étant au moins l'une des unités suivantes :
    une unité de commande de freinage en mode normal (BCU) configurée pour générer un signal de commande de force de freinage pour l'EMAC pendant un mode de fonctionnement normal ; et
    une unité de commande de freinage en mode d'urgence (eBCU) configurée pour générer un signal de commande de force de freinage pour l'EMAC pendant un fonctionnement en mode d'urgence.
  4. Système de freinage actionné électriquement selon la revendication 3, l'unité de commande de freinage disposée dans la LRU commune étant la BCU, et le système comprenant en outre :
    une unité de commande de freinage en mode d'urgence (eBCU) configurée pour générer un signal de commande de force de freinage pour l'EMAC pendant un mode de fonctionnement d'urgence, l'eBCU étant disposée à distance de la BCU.
  5. Système de freinage actionné électriquement selon la revendication 3, l'unité de commande de freinage disposée dans la LRU commune étant l'eBCU, et le système comprenant en outre :
    une unité de commande de freinage en mode normal (BCU) configurée pour générer un signal de commande de force de freinage pour l'EMAC pendant un mode de fonctionnement normal, la BCU étant disposée à distance de l'eBCU.
  6. Système de freinage actionné électriquement selon la revendication 3, la BCU et l'eBCU étant toutes deux disposées dans la LRU commune.
  7. Système de freinage actionné électriquement selon l'une quelconque des revendications 4 à 6, la BCU pouvant fonctionner sur un canal de freinage normal, et l'eBCU pouvant fonctionner sur un canal de freinage d'urgence.
  8. Système de freinage actionné électriquement selon l'une quelconque des revendications précédentes, l'EMAC comprenant un premier dispositif de commande de moteur pour générer un premier signal d'entraînement pour l'EMAbrake, et un second dispositif de commande de moteur pour générer un second signal d'entraînement pour l'EMAbrake, de préférence le premier dispositif de commande de moteur et le second dispositif de commande de moteur étant différents afin d'offrir une protection contre une défaillance en mode commun des premier et second dispositifs de commande de moteur.
  9. Système de freinage actionné électriquement selon la revendication 8, le premier dispositif de commande de moteur pouvant fonctionner sur un canal de commande de moteur normal, et le second dispositif de commande de moteur pouvant fonctionner sur un canal de commande de moteur d'urgence.
  10. Système de freinage actionné électriquement selon les revendications 7 et 9, la BCU étant configurée pour communiquer avec le premier dispositif de commande de moteur et non avec le second dispositif de commande de moteur, et l'eBCU étant configurée pour communiquer avec le second dispositif de commande de moteur et non avec le premier dispositif de commande de moteur, de préférence le canal de freinage normal et le canal de commande de moteur normal étant couplés de manière à former un canal normal, et le canal de freinage d'urgence et le canal de commande de moteur d'urgence étant couplés de manière à former un canal d'urgence, et le système comprenant en outre un commutateur pour commuter entre le canal normal et le canal d'urgence.
  11. Système de freinage actionné électriquement selon les revendications 7 et 9, la BCU étant configurée pour communiquer soit avec le premier dispositif de commande de moteur, soit avec le second dispositif de commande de moteur, et l'eBCU étant configurée pour communiquer soit avec le premier dispositif de commande de moteur, soit avec le second dispositif de commande de moteur, et de préférence comprenant en outre un premier commutateur pour commuter entre les canaux de frein normal et d'urgence, et un second commutateur pour commuter entre les canaux de commande de moteur normal et d'urgence, de préférence le premier commutateur et le second commutateur pouvant commuter indépendamment.
  12. Système de freinage actionné électriquement selon l'une quelconque des revendications 9 à 11, comprenant en outre soit un commutateur source couplé de manière opérationnelle entre les canaux de commande de moteur normal et d'urgence et l'EMAbrake pour commuter la commande EMAbrake en fonction du canal de commande de moteur sélectionné, soit une porte OU couplée de manière opérationnelle entre les canaux de commande de moteur normal et d'urgence et l'EMAbrake pour commander l'EMAbrake en fonction du canal de commande de moteur fonctionnel.
  13. Système de freinage actionné électriquement selon l'une quelconque des revendications 7 à 12, la BCU comprenant des canaux de commande de freinage redondants pour la communication avec les commandes du poste de pilotage et l'avionique de l'aéronef via un bus de données respectif.
  14. Système de freinage actionné électriquement selon l'une quelconque des revendications 8 à 13, le premier dispositif de commande de moteur et le second dispositif de commande de moteur comprenant chacun du matériel pour générer un signal de modulation de largeur d'impulsion, et/ou le premier dispositif de commande de moteur et le second dispositif de commande de moteur comprenant chacun un matériel différent choisi parmi le groupe comprenant : un microprocesseur, un microcontrôleur, un processeur de signaux numériques, un circuit intégré spécifique à une application, un dispositif logique programmable, un dispositif logique programmable complexe, un réseau de portes programmables sur site et un circuit de commutation électronique discret à transistors.
  15. Aéronef comprenant un système de freinage actionné électriquement selon n'importe quelle revendication précédente.
  16. Aéronef selon la revendication 15, comprenant en outre un train d'atterrissage ayant une branche principale et un ensemble de frein de roue, et un routeur pour acheminer des communications numériques entre un bus de données descendant la branche principale et une LRU commune associée à l'ensemble de frein de roue, de préférence le routeur étant situé adjacent à une extrémité inférieure de la branche principale du train d'atterrissage, et de préférence comprenant en outre une pluralité des LRU communes ayant chacune un EMAbrake respectif, une pluralité des EMAbrakes pouvant fonctionner pour freiner la même roue du train d'atterrissage.
EP14195206.9A 2013-11-27 2014-11-27 Système de freinage électrique d'avion Active EP2878503B1 (fr)

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Families Citing this family (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2520693A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system
GB2520694A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system
GB2520696A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system
FR3054201B1 (fr) * 2016-07-25 2018-07-27 Safran Landing Systems Systeme de freinage d'aeronef a haut niveau de disponibilite
US10300896B2 (en) * 2016-10-10 2019-05-28 Textron Innovations, Inc. Brake system for aircraft
US10155583B2 (en) 2016-10-14 2018-12-18 Goodrich Corporation Aircraft control system architecture
US10259571B2 (en) 2016-12-06 2019-04-16 Goodrich Corporation Electrically controlled park and emergency valve assembly
US10272888B2 (en) * 2016-12-09 2019-04-30 Goodrich Corporation Systems and methods for aircraft emergency and park brakes
FR3061139B1 (fr) * 2016-12-23 2019-05-31 Safran Landing Systems Architecture de systeme de freinage pour aeronef
FR3063278B1 (fr) * 2017-02-24 2019-04-19 Safran Landing Systems Systeme d'extension de secours d'atterrisseur d'aeronef
US10131329B1 (en) * 2017-06-23 2018-11-20 Goodrich, Corporation Brake system power arbitration
CN109823522B (zh) * 2017-11-23 2024-02-23 成都凯天电子股份有限公司 多冗余度起落架电动收放控制器
FR3075491B1 (fr) * 2017-12-14 2019-12-20 Safran Landing Systems Harnais electrique
US10829211B2 (en) * 2018-04-23 2020-11-10 Goodrich Corporation Local digital conversion for force and position signals for electric actuation control
CN109334959B (zh) * 2018-09-28 2024-03-26 山河星航实业股份有限公司 一种飞机刹车控制系统及方法
US11492103B2 (en) 2019-04-08 2022-11-08 Goodrich Corporation Distributed brake control systems and methods for high efficiency antiskid performance
FR3096326B1 (fr) * 2019-05-23 2022-10-28 Safran Landing Systems Système de freinage d’aéronef avec dispositifs de commande dissimilaires et module logiciel utilisé en cas de défaillance
US11691604B2 (en) 2020-08-06 2023-07-04 Gulfstream Aerospace Corporation Vehicle braking capability determination by braking with fewer than all available braking wheels
US20220097832A1 (en) * 2020-09-29 2022-03-31 Goodrich Corporation Hybrid brake system
US11999468B2 (en) 2022-02-10 2024-06-04 Goodrich Corporation Hybrid brake systems and methods
US11970263B2 (en) 2022-02-10 2024-04-30 Goodrich Corporation Hybrid brake systems and methods for load cell calibration
US11702193B1 (en) 2022-04-28 2023-07-18 Beta Air, Llc Systems and methods for an electric vertical takeoff and landing aircraft braking system

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1084949A2 (fr) * 1999-09-13 2001-03-21 The B.F. Goodrich Company Frein multidisques pour avions
GB2444630A (en) * 2006-12-04 2008-06-11 Boeing Co Brake Status Indicator for an Electric Braking System of a Vehicle.

Family Cites Families (45)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA2214156C (fr) * 1996-09-13 2003-07-15 New York Air Brake Corporation Unite de commande de frein de locomotive avec boucle d'interdiction de phase de freinage dynamique
US6003640A (en) 1997-05-09 1999-12-21 The B.F. Goodrich Company Electronic braking system with brake wear measurement and running clearance adjustment
US6115656A (en) 1997-06-17 2000-09-05 Mcdonnell Douglas Corporation Fault recording and reporting method
DE19828331C1 (de) 1998-06-25 2000-03-02 Continental Ag Verfahren zum Betreiben einer elektromechanischen Bremsanlage
US6183051B1 (en) 1999-02-01 2001-02-06 Aircraft Braking Systems Corp. Fail safe electrical brake control system for aircraft
US6296325B1 (en) 1999-07-15 2001-10-02 The B. F. Goodrich Company Method to connect and distribute power to an electromechanical braking system
DE60015134T2 (de) * 1999-07-14 2005-03-10 Goodrich Corp., Akron Bremssystem mit stromversorgung, -verteilung und -redundanz
US6402259B2 (en) 1999-07-14 2002-06-11 Goodrich Corporation Electromechanical braking system with power distribution and redundancy
JP3872242B2 (ja) 1999-09-21 2007-01-24 トヨタ自動車株式会社 ブレーキ制御装置
US20050110339A1 (en) 2003-11-26 2005-05-26 Kolberg David A. EMAC arrangement for reducing wiring requirements
US7237748B2 (en) 2003-12-15 2007-07-03 Delos Aerospace, Llc Landing gear method and apparatus for braking and maneuvering
US7356336B2 (en) 2004-01-06 2008-04-08 The Boeing Company Systems and methods of recording events onboard a vehicle
US20060108867A1 (en) 2004-09-17 2006-05-25 Mihai Ralea Electromechanical braking system with electrical energy back-up and regenerative energy management
US20060061210A1 (en) * 2004-09-17 2006-03-23 Mihai Ralea Electromechanical braking system with electrical energy back-up
EP1845000A3 (fr) 2006-04-11 2010-03-24 Goodrich Corporation Contrôleur pour système de freinage électromécanique doté d'un réglage du jeu fonctionnel et procédé
US9656641B2 (en) 2006-08-04 2017-05-23 The Boeing Company Aircraft electrical brake control system architecture
EP2076435A2 (fr) * 2006-10-24 2009-07-08 Goodrich Corporation Unité de mesure d'actionnement de frein d'avion
GB0623804D0 (en) * 2006-11-29 2007-01-10 Dunlop Aerospace Ltd A Braking system for an aircraft and a method of monitoring braking for an air
US9108602B2 (en) * 2006-12-05 2015-08-18 The Boeing Company Parking brake control for an aircraft having an electric brake system
US20080258548A1 (en) 2007-04-18 2008-10-23 Bill May Aircraft brake control architecture having improved antiskid redundancy
ATE485981T1 (de) 2007-05-19 2010-11-15 Goodrich Corp Flugzeugbremsen-steuerungsarchitektur mit verbesserter antirutsch-redundanz
EP2167357B1 (fr) 2007-05-19 2016-03-30 Goodrich Corporation Commande de frein indépendante d'un train d'atterrissage ordinaire pour avion
JP5013978B2 (ja) 2007-06-11 2012-08-29 サンデン株式会社 自動販売機
GB0806660D0 (en) 2008-04-11 2008-05-14 Airbus Uk Ltd Aircraft landing gear
US8550572B2 (en) 2008-05-05 2013-10-08 Goodrich Corporation Electromechanical brake system with distributed architecture
US20090276133A1 (en) 2008-05-05 2009-11-05 Goodrich Corporation Aircraft brake control system and method
US8590985B2 (en) 2008-09-30 2013-11-26 Goodrich Corporation Method to degrade braking modes
US8112213B2 (en) 2009-04-24 2012-02-07 Goodrich Corporation Electric brake architecture with dissimilar emergency braking path
US8565939B2 (en) 2009-04-30 2013-10-22 Goodrich Corporation Distributed pedal system for aircraft
US9216720B2 (en) 2009-04-30 2015-12-22 Goodrich Corporation Differential emergency/park electric brake system
US9227608B2 (en) 2009-08-12 2016-01-05 Meggitt Aircraft Braking Systems Decentralized electric brake system
FR2952009B1 (fr) 2009-10-30 2011-12-09 Messier Bugatti Architecture de systeme de freinage electromecanique
FR2954753B1 (fr) * 2009-12-24 2012-03-09 Messier Bugatti Architecture dissymetrique de freinage electrique pour aeronef.
CN102802996B (zh) 2010-03-02 2015-03-04 万国卡车知识产权有限公司 再生制动系统重置特征以及对混合式电动车辆和电动车辆的自适应校准
US20110226569A1 (en) 2010-03-19 2011-09-22 Hydro-Aire, Inc. Electronic motor actuators brake inhibit for aircraft braking system
US8489302B2 (en) 2010-09-14 2013-07-16 Goodrich Corporation Systems and methods for dynamically stable braking
US9022316B2 (en) 2010-11-24 2015-05-05 Borealis Technical Limited System and method for failsafe operation of aircraft ground movement system
US9028014B2 (en) 2010-12-08 2015-05-12 Goodrich Corporation System and method for providing indication of braking for electric brakes
FR2970387B1 (fr) 2011-01-10 2013-12-13 Messier Bugatti Actionneur electromecanique a double excitation.
US9669810B2 (en) 2012-01-10 2017-06-06 Honeywell International Inc. Brake assembly including independently activatable brake actuators
CN104540732B (zh) * 2012-02-09 2018-02-06 莫戈公司 致动器系统和方法
FR2988373B1 (fr) 2012-03-21 2014-04-25 Messier Bugatti Dowty Systeme de freinage electromecanique pour aeronef
GB2520696A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system
GB2520693A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system
GB2520694A (en) * 2013-11-27 2015-06-03 Airbus Operations Ltd Aircraft electric braking system

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1084949A2 (fr) * 1999-09-13 2001-03-21 The B.F. Goodrich Company Frein multidisques pour avions
GB2444630A (en) * 2006-12-04 2008-06-11 Boeing Co Brake Status Indicator for an Electric Braking System of a Vehicle.

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CN110329496A (zh) 2019-10-15
PL2878503T3 (pl) 2019-11-29
US10259570B2 (en) 2019-04-16
GB2520696A (en) 2015-06-03
US20150291280A1 (en) 2015-10-15
CN104670481B (zh) 2019-08-13
EP2878503A1 (fr) 2015-06-03
GB201320941D0 (en) 2014-01-08

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